DESIGN OF LUNAR-GRAVITY-ASSISTED ESCAPE MANEUVERS

被引：0

作者：

Casalino, Lorenzo ^{[1
]}

Lantoine, Gregory ^{[2
]}

机构：

[1] Politecn Torino, DIMEAS, Corso Duca Abruzzi 24, I-10129 Turin, Italy

[2] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA

来源：

ASTRODYNAMICS 2017, PTS I-IV | 2018年 / 162卷

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

Lunar gravity assist is a means to boost the energy and C3 of an escape maneuver. Two approaches are applied and tested for the design of trajectories aimed at Near-Earth asteroids. Maneuvers with two lunar gravity assists are considered and analyzed. Indirect optimization of the heliocentric leg is combined to an approximate analytical treatment of the geocentric phase for short escape maneuvers. The results of pre-computed maps of escape C3 are used for the design of longer sun-perturbed escape sequences. Features are compared and suggestions about a combined use of the approaches are presented. The techniques are efficiently applied to the design of a mission to a near-Earth asteroid.

引用

页码：663 / 675

页数：13

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